A seal structure for sealing a gap between a first member and a second member of an aircraft includes: a plate spring-shaped first elastic seal; and a second elastic seal. When the first member and the second member are stationary with respect to each other, the first elastic seal elastically deforms between the first member and the second member to seal the gap, whereas the second elastic seal does not seal the gap. When the first member and the second member move closer to each other and the first elastic seal is elastically deformed, the second elastic seal elastically deforms between the first member and the second member to seal the gap.

A suspension device for suspending, for example, a turbine engine to a pylon, the device comprising a first unit interposed between a first lug and a second lug of a second unit, the first unit having a bore for passing an axle running through first and second bushings mounted respectively in said first and second lugs; and a clamping unit interacting with the axle. The device further comprising a third bushing mounted in the second lug and having radial centering means which interact with the complementary centering means of a head section of the axle; and a fourth axially slidably mounted bushing, biased axially by the clamping unit, and comprising radial centering means which interact with complementary centering means of the first bushing.

The present disclosure is applicable to all vehicles having an engine mounted therein. In one embodiment, an aft mount system for a gas turbine engine is disclosed. The aft mount system includes a vehicle chassis and at least one flexible mounting member disposed within the vehicle chassis, wherein when a gas turbine engine is received within the vehicle chassis, an exhaust portion of the gas turbine engine is substantially mounted within the vehicle chassis through engagement with the at least one flexible mounting member.

To allow the attachment of an engine of the Open Rotor Puller type to the rigid structure of an attachment pylon, an attachment structure comprises a first attachment structure shifted forwards with respect to the center of gravity of the engine and connected to the rigid structure through a pyramid, a second attachment structure laid out at the rear with respect to the first attachment structure and extending in a plane of a first stringer of the rigid structure, and a third attachment structure laid out at the rear with respect to the second attachment structure. The second attachment structure comprises two engine attachments for recovering the moment along the axis of the engine, laid out on either side of a horizontal symmetry plane of the engine.

A multi-material component is provided including two members formed of different materials joined together at a multi-material join. The two members have complementary protrusions that form a multi-material join with a zig-zag interface, such that a tension between them is experienced in at least part as a shear force at the interface between the protrusions. The component further includes a third member connected to the first member by a lattice, which is capable of elastic deformation so as to substantially isolate the interface between the complementary protrusions from deformation of the third member such as that caused by thermal expansion. Methods of designing and constructing such a component in a single piece via additive manufacturing are provided. The component is particularly suitable for use in pylons connecting jet engines to aircraft wings.

Housing a conduit of a thermal protection system of a rigid structure of an attachment pylon in an aircraft propulsion assembly within a box of the rigid structure, so as to take advantage of the volume within the rigid structure. The elements forming the conduits thus form an integral part of the rigid structure and can thus play a structural role.

An aircraft comprising a fuselage extending along a longitudinal axis between a fore section and an aft section, wings mounted to the fuselage, a tail unit mounted to the aft section of the fuselage, and a first propulsion unit and a second propulsion unit both mounted to the aft section of the fuselage in such a way that a first axis of rotation of the first propulsion unit and a second axis of rotation of the second propulsion unit both extend in a vertical center plane spanned by the longitudinal axis and a yaw axis. The provided centerline mounted double-engine aircraft allows for a simple manufacture, maintenance and retrofit of the engines, in that the first propulsion unit and/or the second propulsion unit are arranged outside the fuselage.

A cradle for supporting an aircraft turbine engine, said cradle comprising an attachment interface for attaching a gas generator of the turbine engine. The cradle is produced in at least two portions comprising: an upper half-cradle, which is designed to be attached to a wing of the aircraft, a lower half-cradle, which is movable between a position in which it is connected to the upper half-cradle and a position in which it is disconnected from the upper half-cradle, and which comprises at least a portion of the attachment interface for attaching the gas generator, a guide configured for slidably guiding the lower half-cradle between the connected and disconnected positions thereof, and at least one lock for locking the lower half-cradle in the connected position thereof.

A jet engine support structure includes an inboard support fitting that is configured to be operatively attached to the jet engine, an outboard support fitting that is configured to be operatively attached to the jet engine, an inboard longeron that is configured to be attached to the inboard support fitting and an exterior underside surface of an aircraft wing, an outboard longeron that is configured to be attached to the outboard support fitting and the exterior underside surface of the wing, and a drag brace fitting that is configured to be attached to the inboard longeron and the outboard longeron and operatively attached to the jet engine. These component parts are employed in operatively attaching the jet engine to the aircraft wing. The same set of component parts is employed in operatively attaching the jet engine to either a left side or port side wing or to operatively attach a jet engine to a right side or starboard side wing. The construction of the longerons enable their attachment to the underside surface of the wing using fasteners already used in the wing construction.

A mounting system for a gas turbine engine includes a low pressure turbine section, a first bearing, a mid-turbine frame, and a rear mount. The first bearing supports at least a portion of the low pressure turbine section. The mid-turbine frame supports the first bearing. The rear mount is connected to the mid-turbine frame and is configured to react loads from the gas turbine engine.